Tests of 12-ft span wing at Mach numbers up to 0.69; max lift coefficient varied with Mach number and was affected by sharpness of leading edge at higher Mach numbers; formation of extensive local supersonic flow regions caused center of pressure to move forward at high angles of attack and high Mach numbers.
Effects of compressibility on lift, pressure, and load characteristics of tapered wing of NACA 66-series airfoil sections
Nat Advisory Committee Aeronautics -- Tech Note
1948
59 pages
Bibliography
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Engineering Index Backfile | 1949
|